Solid fuel turbine engine

Abstract

A solid fuel turbine engine comprises a centrally disposed axially extending shaft having an annular combustion chamber disposed thereabout intermediate the ends thereof. A compressor is mounted at one end of the shaft for delivering air to the combustion chamber to provide the principal source of oxygen for combustion and a turbine is mounted at the other end of the shaft. The turbine is driven by combustion gases and drives the compressor. An annular solid fuel charge is disposed in the combustion chamber for producing combustion gases.

I claim: 
     
       1. A solid fuel turbine engine comprising a centrally disposed axially extending rotatable compressor drive shaft,   an annular combustion chamber having an inlet end and an outlet end and disposed about said compressor drive shaft intermediate the ends thereof,   the annular configuration of said combustion chamber being defined by a pair of radially spaced, cylindrical walls which are concentric with one another and with said shaft,   an annular solid fuel charge in said combustion chamber for producing combustion gases,   an expansion chamber at the outlet end of said combustion chamber and axially aligned therewith,   a compressor on said shaft at the inlet end of said combustion chamber for delivering air to said combustion chamber to provide the principal source of oxygen for combustion, and   a turbine on the other end of said shaft at the outlet end of said combustion chamber driven by said combustion gases and driving aid compressor.   
     
     
       2. An engine in accordance with claim 1 including a compressed air bypass conduit communicating with the inlet end of said combustion chamber and with the expansion chamber in said combustion chamber for bypassing the solid fuel charge, and a valve in said conduit for controlling the flow of air therein. 
     
     
       3. An engine in accordance with claim 1 wherein said solid propellant is provided with a discrete pyrotechnic igniter adjacent an initial burn surface at a compressed air inlet end of said propellant.